EP3502438A1 - Kompressorsteuerung - Google Patents

Kompressorsteuerung Download PDF

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Publication number
EP3502438A1
EP3502438A1 EP17208567.2A EP17208567A EP3502438A1 EP 3502438 A1 EP3502438 A1 EP 3502438A1 EP 17208567 A EP17208567 A EP 17208567A EP 3502438 A1 EP3502438 A1 EP 3502438A1
Authority
EP
European Patent Office
Prior art keywords
guide vane
variable guide
range
engine
operational axis
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP17208567.2A
Other languages
English (en)
French (fr)
Inventor
Senthil Krishnababu
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP17208567.2A priority Critical patent/EP3502438A1/de
Priority to EP18830177.4A priority patent/EP3728816A1/de
Priority to PCT/EP2018/084598 priority patent/WO2019121252A1/en
Priority to US16/767,325 priority patent/US11365690B2/en
Priority to RU2020120154A priority patent/RU2744116C1/ru
Priority to CN201880082106.7A priority patent/CN111527293B/zh
Priority to CA3083332A priority patent/CA3083332C/en
Publication of EP3502438A1 publication Critical patent/EP3502438A1/de
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/057—Control or regulation
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/02—Purpose of the control system to control rotational speed (n)
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/01—Purpose of the control system
    • F05D2270/10—Purpose of the control system to cope with, or avoid, compressor flow instabilities
    • F05D2270/101—Compressor surge or stall
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/304—Spool rotational speed

Definitions

  • the present disclosure relates to control of a compressor.
  • the disclosure is concerned with control of a compressor for a gas turbine engine.
  • a gas turbine comprises a turbine and a compressor driven by the turbine.
  • a compressor may consist of multiple stages of stator vanes which are non-rotatable about the operational axis, and rotor blades which are rotatable about the operational axis.
  • the gas turbine is subjected to varying operating conditions resulting in different aerodynamic flow conditions within the compressor.
  • variable guide vanes In order to adapt the compressor performance to different flow conditions, it is known to provide the compressor with variable guide vanes (VGV).
  • VV variable guide vanes
  • the variable guide vanes are pivotable/rotatable about their longitudinal axis in order to adjust their angle relative to the operational axis of the engine (i.e. the axial flow direction through the compressor), and hence relative to rotor blades downstream.
  • Operational flow conditions may induce a stall condition during start-up and at off-design conditions. This may result in aerodynamic noise, loss of efficiency and excessive rotor vibration.
  • compressor stall may be reduced by rotating the variable guide vanes to increase the blade angle relative to the operational axis and reduce the compressor throat area, thus reducing the mass flow of air through the compressor.
  • the compressor may also comprise an array (48) of compressor blades coupled to a rotatable engine shaft (22) which extends along the operational axis (20), with a first variable guide vane (8a) axially spaced apart from the compressor blade array (48) along the operational axis (20), wherein the first variable guide vane (8a) is rotatably mounted at a first location (202) on the casing (50), having a vane axis of rotation (121) at right angles to the operational axis (20).
  • the first variable guide vane (8a) may be coupled to an adjustment drive (154) operable to rotate the first variable guide vane (8a) about its axis of rotation (121) to a range (A-D) of angles relative to the operational axis (20).
  • the controller (300) may be operable to control the rotation of the first variable guide vane (8a) in dependence of engine shaft speed wherein over a first range (A-B) and third range (C-D) of engine shaft speed the angle of the first variable guide vane (8a) relative to the operational axis (20) decreases (R1) with increasing engine speed and/or increases (R2) with decreasing engine speed.
  • Over a second range (B-C) of engine shaft speeds the angle of the first variable guide vane (8a) relative to the operational axis (20) increases (R2) with increasing engine speed and/or decreases (R1) with decreasing engine speed.
  • a gas turbine engine comprising a compressor having a casing (50) which extends along, and is centred on, an operational axis (20).
  • the compressor may also comprise an array (48) of compressor blades coupled to a rotatable engine shaft (22) which extends along the operational axis (20), a first variable guide vane (8a) axially spaced apart from the compressor blade array (48) along the operational axis (20), wherein the first variable guide vane is rotatably mounted at a first location (202) on the casing (50), having a vane axis of rotation (121) at right angles to the operational axis (20).
  • the first variable guide vane (8a) may be coupled to an adjustment drive (154) operable to rotate the first variable guide vane (8a) about its axis of rotation (121) to a range (A-D) of angles relative to the operational axis (20).
  • the compressor and/or engine may also comprise a controller (300) operable to control the rotation of the first variable guide vane (8a) in dependence of engine shaft speed wherein : over a first range (A-B) and third range (C-D) of engine shaft speed the angle of the first variable guide vane (8a) relative to the operational axis (20) may decrease (R1) with increasing engine speed and/or increases (R2) with decreasing engine speed. Over a second range (B-C) of engine shaft speeds the angle of the first variable guide vane (8a) relative to the operational axis (20) may increase (R2) with increasing engine speed and/or decreases (R1) with decreasing engine speed.
  • the method may comprise controlling the rotation of the first variable guide vane (8a) in dependence of engine shaft speed wherein over a first range (A-B) and third range (C-D) of engine shaft speed the angle of the first variable guide vane (8a) relative to the operational axis (20) may decrease (R1) with increasing engine speed and/or increase (R2) with decreasing engine speed. Over a second range (B-C) of engine shaft speeds the angle of the first variable guide vane (8a) relative to the operational axis (20) may increase (R2) with increasing engine speed; and/or decrease (R1) with decreasing engine speed.
  • the second range (B-C) of engine shaft speeds may be between first range (A-B) and third range (C-D).
  • the first range (A-B) may have a maximum value no greater than the minimum value of the second range (B-C); and the second range (B-C) may have a maximum value no greater than the minimum value of the third range (C-D).
  • the rate of change of angle per unit change of engine shaft speed of the first variable guide vane (8a) relative to the operational axis (20) may be greater in the third range (C-D) than in the first range (A-B).
  • the first range (A-B) may be from 0 to 80% engine shaft speed.
  • the second range may be from 80% to 90% engine shaft speed.
  • the third range may be from 90% to 100% engine shaft speed.
  • the first range (A-B) may be from 0% to no more than 80% engine shaft speed.
  • the second range may be from no less than 80% to no more than 95% engine shaft speed.
  • the third range may be from no less than 95% to no more than 100% engine shaft speed.
  • the compressor may further comprise a second variable guide vane (8b) axially spaced apart from the first variable guide vane (8a) along the operational axis (20), wherein the second variable guide vane (8b) is rotatably mounted at a second location (204) on the casing (50), having a vane axis of rotation (121b) at right angles to the operational axis (20); and the second variable guide vane (8b) is coupled to the adjustment drive (154); operable to rotate the second variable guide vane (8b) about its axis of rotation (121) to a range of angles relative to the operational axis (20) at the same time as rotating the first variable guide vane.
  • a second variable guide vane (8b) axially spaced apart from the first variable guide vane (8a) along the operational axis (20), wherein the second variable guide vane (8b) is rotatably mounted at a second location (204) on the casing (50), having a vane axis of rotation (121b) at right angles to the operational axis
  • the method may further comprise the step of controlling the rotation of the second variable guide vane (8b) in dependence of engine shaft speed wherein : over the first range (A-B), second range (B-C) and third range (C-D) of engine shaft speed the angle of the second variable guide vane (8b) relative to the operational axis (20) : decreases (R1) with increasing engine speed; and/or increases (R2) with decreasing engine speed.
  • the rotation of the variable guide vanes may be controlled such that : over the first range (A-B) of engine shaft speeds the angle of the first variable guide vane (8a) and second variable guide vane (8b) relative to the operational axis (20) changes at the same rate.
  • the rotation of the variable guide vanes may be controlled such that : over the third range (C-D) of engine shaft speeds the angle of the first variable guide vane (8a) changes at a greater rate than the second variable guide vane (8b).
  • the adjustment drive (154) may comprise one actuator (156) coupled to both the first variable guide vane (8a) and second variable guide vane (8b).
  • the adjustment drive (154) may comprise a first actuator (156) and second actuator (156'), the first actuator (156) coupled to the first variable guide vane (8a); and the second actuator (156') coupled to the second variable guide vane (8b); and the controller (300) is operable to control both of the actuators (156, 156') of the adjustment drive (154).
  • a tangible non-transient computer-readable storage medium having recorded thereon instructions which when implemented by a controller for a gas turbine according to the present disclosure causes the controller to perform a method of controlling the gas turbine according to the present disclosure.
  • a system for performing a variable guide vane schedule for improved compressor operability is designed to induce one or several changes of direction of at least one variable guide vane stage.
  • the schedule is also designed so that the angle of at least one variable vane stage can be varied relative to other variable guide vane stages. This provides sufficient control to air flow to avoid stall.
  • control may be achieved by gradually closing the first stage variable guide vane while gradually opening the later variable guide vane stages over predetermined engine operating conditions. In this way loading on the downstream rotor blades is reduced thus avoiding a stall condition and other deleterious blade dynamic issues.
  • the present disclosure relates to a controller (300) for a gas turbine engine (10), the gas turbine engine (10) comprising a compressor.
  • the present disclosure also relates to a gas turbine engine, a method of controlling the gas turbine engine, and tangible non-transient computer-readable storage medium
  • Figures 1 to 4 show an engine and compressor arrangement to which features of the present disclosure may be applied.
  • features of the present disclosure may be applied to other arrangements also, for example containing different or alternative combinations of features.
  • FIG. 1 shows an example of a gas turbine engine 10 in a sectional view.
  • the gas turbine engine 10 comprises, in flow series, an inlet 12, a compressor or compressor section 14, a combustor section 16 and a turbine section 18 which are generally arranged in flow series and generally about and in the direction of a rotational axis 20.
  • the rotational axis may also be termed the "operational axis", the direction of flow through the compressor being generally aligned with the operational/rotational axis.
  • the gas turbine engine 10 further comprises a shaft 22 which is rotatable about the rotational axis 20 and which extends longitudinally through the gas turbine engine 10.
  • the shaft 22 drivingly connects the turbine section 18 to the compressor section 14.
  • air 24 which is taken in through the air inlet 12 is compressed by the compressor 14 and delivered to the combustion section or burner section 16.
  • the burner section 16 comprises a burner plenum 26, one or more combustion chambers 28 extending along a longitudinal axis 35 and at least one burner 30 fixed to each combustion chamber 28.
  • the combustion chambers 28 and the burners 30 are located inside the burner plenum 26.
  • the compressed air passing through the compressor 14 enters a diffuser 32 and is discharged from the diffuser 32 into the burner plenum 26 from where a portion of the air enters the burner 30 and is mixed with a gaseous or liquid fuel.
  • the air/fuel mixture is then burned and the combustion gas 34 or working gas from the combustion is channelled through the combustion chamber 28 to the turbine section 18 via a transition duct 17.
  • This exemplary gas turbine engine 10 has a cannular combustor section arrangement 16, which is constituted by an annular array of combustor cans 19 each having the burner 30 and the combustion chamber 28, the transition duct 17 has a generally circular inlet that interfaces with the combustor chamber 28 and an outlet in the form of an annular segment.
  • An annular array of transition duct outlets form an annulus for channelling the combustion gases to the turbine 18.
  • the turbine section 18 comprises a number of blade carrying discs 36 attached to the shaft 22.
  • two discs 36 each carry an annular array of turbine blades 38 are shown.
  • the number of blade carrying discs could be different, i.e. only one disc or more than two discs.
  • guiding vanes 40 which are fixed to a stator 42 of the gas turbine engine 10, are disposed between the stages of annular arrays of turbine blades 38. Between the exit of the combustion chamber 28 and the leading turbine blades 38 inlet guiding vanes 44 are provided and turn the flow of working gas onto the turbine blades 38.
  • the combustion gas 34 from the combustion chamber 28 enters the turbine section 18 and drives the turbine blades 38 which in turn rotate the shaft 22.
  • the guiding vanes 40, 44 serve to optimise the angle of the combustion or working gas 34 on the turbine blades 38.
  • the turbine section 18 drives the compressor 14, i.e. particularly a compressor rotor, via the shaft 22.
  • the compressor 14 comprises an axial series of vane stages 46, or guide vane stages 46, and rotor blade stages 48.
  • the rotor blade stages 48 comprise a rotor disc supporting an annular array of blades.
  • the compressor 14 also comprises a casing 50 that surrounds the rotor blade stages 48 and supports the guide vane stages 46.
  • the casing 50 extends along, and is centred on, the operational axis 20.
  • the guide vane stages 46 include an annular array of radially extending guide vanes 7 that are mounted to the casing 50.
  • the guide vanes 7, hereinafter also referred to as the vanes 7, are provided to present gas flow at an optimal angle for the blades of the rotor blade stage 48 that is present adjacent to and downstream of, with respect to a flow direction of the air 24 along the compressor 14 at a given engine operational point.
  • the casing 50 defines a radially outer surface 52 of the passage 56 of the compressor 14.
  • the guide vane stages 46 and the rotor blade stages 48 are arranged in the passage 56, generally alternately axially.
  • the passage 56 defines a flow path for the air through the compressor 14 and is also referred to as an axial flow path 56 of the compressor 14.
  • the air 24 coming from the inlet 12 flows over and around the guide vane stages 46 and the rotor blade stages 48.
  • a radially inner surface 54 of the passage 56 is at least partly defined by a rotor drum 53 of the rotor which is partly defined by the annular array of blades.
  • Some of the guide vane stages 46 have variable guide vanes 8 (shown as vanes 8a, 8b, 8c, 8d), where the angle of the guide vanes 8, about their own longitudinal axis, can be adjusted for angle according to air flow characteristics that can occur at different engine operations conditions.
  • Some of the other guide vane stages 46 have stationary guide vanes 9 where the angle of the guide vanes 9, about their own longitudinal axis, is fixed and thus not adjustable for angle.
  • the present method, apparatus and system is described with reference to the above exemplary turbine engine having a single shaft or spool connecting a single, multistage compressor and a single, one or more stage turbine.
  • the present system and method is equally applicable to two or three shaft engines and which can be used for industrial, aero or marine applications.
  • the cannular combustor section arrangement 16 is also used for exemplary purposes and it should be appreciated that the present technique is equally applicable to gas turbine engines 10 having annular type and can type combustion chambers.
  • the pitch or the angular offset for the individual stages of variable guide vanes 8a-d inside of the compressor wall 50 is controlled via a linkage mechanism 100 which is applied from the outside of the wall.
  • Each individual vane 8a (first stage 46a), 8b (second stage 46b), 8c (third stage 46c), 8d (fourth stage 46d) may be mounted on a spindle 122 to allow angular movement of the vane 8a, 8b.
  • Figure 3 shows an individual vane 8a of the first stage, e.g. the most upstream stage of the compressor and a corresponding lever 120.
  • Figure 4 shows an view along the length of vanes 8a showing how they rotate about their axis of rotation 121.
  • the lever 120 may connect the spindle 122 to a driving ring 140, provided as an adjustment ring, the so called unison ring.
  • a driving ring 140 provided as an adjustment ring, the so called unison ring.
  • Each vane 8 of each stage 46 is connected to its respective unison ring via a lever 120. That is to say, the lever 120 connects the spindle 122 of each vane to a respective driving ring 140, 141, 142, 143.
  • All vanes 8 in a single stage may be connected to the same ring so that all vanes 8 on one stage 46 are adjusted at the same time and with the same angle.
  • Each of the driving rings 140, 141, 142, 143 may be rotated via a push rod 150, one per ring, by a distributor drive 154.
  • the distributor drive may comprise only a single actuator (i.e. a drive). Hence a single drive may provide an input to act on all of the push rods 150, unison rings 140-143 and hence guide vanes.
  • the distributor drive may comprise two or more actuators.
  • one actuator may drive one or more unison rings and the other actuator drives the remaining unison ring(s).
  • multiple drives may provide an input to act on all of the push rods 150, unison rings 140-143 and hence guide vanes.
  • the rotational movement of the driving rings 140, 141, 142, 143 may be applied via the lever 120 as a rotational movement as indicated via arrow m2 to the lever 120 of each vane 8a to 8d.
  • the movement of the distributor drive shaft 152 results in a rotation of vanes 8a to 8d as indicated in Figures 3, 4 .
  • a gas turbine engine 10 comprises a compressor having a casing 50 which extends along, and is centred on, an operational axis 20.
  • An array 48 of compressor blades coupled to a rotatable engine shaft 22 extend along the operational axis 20, and a first variable guide vane 8a is axially spaced apart from the compressor blade array 48 along the operational axis 20.
  • the first variable guide vane is rotatably mounted at a first location 202 on the casing 50, having a vane axis of rotation 121 which extends radially from and at right angles to the operational axis 20.
  • the first variable guide vane 8a is coupled to an adjustment drive 154 which is operable to rotate the first variable guide vane 8a about its axis of rotation 121 to a range A-D of angles (i.e. angular orientations) relative to the operational axis 20.
  • the angle of the variable guide vane relative to the operational axis 20 may be considered in terms of the angle a chord line 123 which extends between the vane leading edge and trailing edge makes with the operational axis 20, for example as shown in Figure 4 .
  • stage 46a is operated in concert with the later stages 46b, 46c, 46d.
  • stages 46b, 46c, 46d are in synchronisation with each other, but stage 46a is configured to open and close to a different schedule.
  • the opening/closing of the stages 46b, 46c, 46d is synchronous in that they all open and close at the same time, whereas the opening/closing of the stages 46a is asynchronous relative to the other stages in that the first stage 46a may be opening when the other stages are closing, and may close at a different rate to the other stages. This is best illustrated with reference to Figure 5 .
  • Figure 5 shows a plot of variable guide vane angle plotted against engine speed for vanes 8a, 8b, 8c, 8d of different stages 46a, 46b, 46c, 46d.
  • the vanes are disposed at a first angle relative to the operational axis 20 (and/or direction of flow through the compressor), and as engine speed increases the vanes are rotated relative to the operational axis 20 (for example in direction R2 as shown in Figure 4 ) such that they are at their most "open" configuration at highest engine speed to allow maximum airflow.
  • vanes of the first stage 46a would follow the same pattern, as indicated by the profile marked 8a' in Figure 5 .
  • the profile for the first stage corresponds to the schedule is as shown for 8a in Figure 5 .
  • the gas turbine engine comprises a controller 300 operable to control the rotation of the first variable guide vane 8a in dependence of engine shaft speed, for example as illustrated in Figure 5 .
  • the controller 300 may form part of an engine control unit and may be fitted to any suitable location on or near the engine and/or compressor.
  • the controller 300 is linked to, and operable to control, the distributor drive 154 to thereby control the variable guide vanes 8a, 8b, 8c, 8d.
  • variable guide vanes 8a, 8b, 8c, 8d are actuated/rotated, their orientation, direction of rotation and rotational speed is controlled by the controller 300.
  • the controller 300 is operable to control the rotation of the variable guide vanes 8a such that over a first range (A-B) and third range (C-D) of engine shaft speed the angle of the first variable guide vane 8a relative to the operational axis 20 decreases (i.e. turns in direction R1 as shown in Figure 4 to increase flow area between vanes 8a) with increasing engine speed and/or increases (i.e. turns in direction R2 as shown in Figure 4 to decrease flow area between vanes 8a with decreasing engine speed.
  • the controller 300 may also be operable to control the rotation of the variable guide vanes 8a such that over a second range (B-C) of engine shaft speeds the angle of the first variable guide vane 8a relative to the operational axis 20 increases (i.e. turns in direction R2) with increasing engine speed and/or decreases (i.e. turns in direction R1) with decreasing engine speed.
  • B-C second range
  • a controller 300 operable to rotate the first variable guide vane 8a about its axis of rotation 121 to a range A-D of angles (that is to say angular orientations in directions R1, R2 relative to the operational axis 20.
  • the controller 300 is operable to control the rotation of the first variable guide vane 8a in dependence of engine shaft speed wherein over a first range A-B and third range C-D of engine shaft speed the angle of the first variable guide vane 8a relative to the operational axis 20 decreases (i.e. turns in direction R1 direction with increasing engine speed; and/or increases (i.e. turns in direction R2 with decreasing engine speed.
  • the angle of the first variable guide vane 8a relative to the operational axis 20 increases (i.e. turns in direction R2) with increasing engine speed; and/or decreases (i.e. turns in direction R1) with decreasing engine speed.
  • the first rotational direction R1 is opposite to the second rotational direction R2.
  • variable guide vane 8a may be one of an array of variable guide vanes 8a arranged around the circumference of the casing 50 to form at least part of the first flow stage 46a.
  • a second variable guide vane 8b axially spaced apart from the first variable guide vane 8a along the operational axis 20 wherein the second variable guide vane 8b is rotatably mounted at a second location 204 on the casing 50, having a vane axis of rotation 121b extending radially from and at right angles to the operational axis 20.
  • the second variable guide vane 8b may be coupled to the adjustment drive 154 which is operable to rotate the second variable guide vane 8b about its axis of rotation 121 to a range A-D of angles (angular orientations) relative to the operational axis 20 at the same time as rotating the first variable guide vane 8a.
  • variable guide vanes 8a, 8b do not provide sufficient compression to enable the air flow to pass through the rear (downstream) vane stages 46c, 46d which become “choked”.
  • flow can separate from aerofoil surfaces causing "stall” and flow reversal in all stages of the compressor 14.
  • surge Normally surges will occur repeatedly until the engine is stopped.
  • Figure 5 illustrates the relative movements of the first stage 46a to later stages 46b, 46c, 46d in an arrangement according to the present disclosure which has been determined to affect air flows such that stall and/or other deleterious air flow conditions will be inhibited from occurring by virtue of a the first stage 46a being restricted compared to the other stages at predetermined engine conditions.
  • variable guide vanes At low speed the variable guide vanes are "closed” (i.e. turned in direction R2 to restrict flow to their maximum extent) and as engine speed increases the variable guide vanes 8a to 8d are opened in direction R1 to their running position in order to pass more flow.
  • a control method controlling the rotation of the first variable guide vane 8a in dependence of engine shaft speed.
  • a first range A-B and third range C-D of engine shaft speed the angle of the first variable guide vane 8a relative to the operational axis 20 decreases (i.e. turns in direction R1) with increasing engine speed and/or increases (i.e. turns in direction R2) with decreasing engine speed.
  • a second range B-C of engine shaft speeds the angle of the first variable guide vane 8a relative to the operational axis 20 increases (i.e. turns in direction R2) with increasing engine speed and/or decreases (i.e. turns in direction R1) with decreasing engine speed.
  • the second range (B-C) of engine shaft speeds may be between first range (A-B) and third range (C-D).
  • the first range (A-B) may have a maximum value no greater than the minimum value of the second range (B-C).
  • the second range (B-C) may have a maximum value no greater than the minimum value of the third range (C-D).
  • the rate of change of angle per unit change of engine shaft speed of the first variable guide vane 8a relative to the operational axis 20 may be greater in the third range (C-D) than in the first range (A-B).
  • the control method may further comprise the step of controlling the rotation of the second variable guide vane 8b in dependence of engine shaft speed wherein over the first range (A-B), second range and third range (C-D) of engine shaft speed the angle of the variable guide vane 8a relative to the operational axis 20 decreases (i.e. turns in direction R1) with increasing engine speed and/or increases (i.e. turns in direction R2) with decreasing engine speed.
  • the rotation of the variable guide vanes may be controlled such that over the third range (C-D) of engine shaft speeds the angle of the first variable guide vane 8a changes at a substantially greater rate than the second variable guide vane 8b.
  • the adjustment drive 154 may comprise one actuator 156 coupled to both the first variable guide vane 8a and second variable guide vane 8b.
  • the adjustment drive 154 may comprise a first actuator 156 and second actuator 156', the first actuator 156 coupled to the first variable guide vane 8a; and the second actuator 156' coupled to the second variable guide vane 8b; and the controller 300 is operable to control both of the actuators 156, 156' of the adjustment drive 154.
  • the second flow stage and the first flow stage are configured such that the vanes 8b of the second flow stage 46b will move by a different amount and/or in a different direction to the variable vanes of the first flow stage 46a at a predetermined flow condition in the compressor 14.
  • the predetermined flow condition may be expressed in terms of engine speed. That is to say, and with reference to Figure 5 , the control method may define that point "B" is at a first % of maximum engine speed, and point "C" is a second % of maximum engine speed.
  • Point “B” may be in the range of 70% to 80% of maximum engine speed, and point C is in the range of 85% to 95% of maximum engine speed.
  • Point “B” may be at 80% of maximum engine speed, and point C may be at 90% of maximum engine speed.
  • point “B” may be at 80% of maximum engine speed, and point C may be at 95% of maximum engine speed.
  • the first engine speed range (A-B) may be from 0 to 80% engine shaft speed.
  • the second engine speed range (B-C) may be from 80% to 90% engine shaft speed.
  • the third range (C-D) may be from 90% to 100% engine shaft speed.
  • the first range (A-B) may be from 0% to no more than 80% engine shaft speed.
  • the second range (B-C) may be no less than 80% to no more than 95% engine shaft speed.
  • the third range (C-D) is from no less than 95% to no more than 100% engine shaft speed.
  • Non-transient computer-readable storage medium having recorded thereon instructions which when implemented by the controller 300 for the gas turbine 10 cause the controller 300 to perform a method of controlling the gas turbine 10 according to the method of the present disclosure.
  • a means to operate a variable guide vane for a compressor to a schedule for improved compressor operability comprises a controller, an engine and/or a method which advantageously closes a first stage variable inlet guide vane of the compressor while opening the other compressor stages. Normally stall is avoided by opening all stages of the compressor, but for compressor flow conditions where this is not effective, the system of the present disclosure provides further resistance to stall.
  • the system of the present disclosure provides an extension to stall/surge margin as well as avoiding/reducing strength of stall should it occur, and also reducing "forcing" of downstream rotor blades to reduce deleterious blade dynamics issues.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Positive-Displacement Air Blowers (AREA)
EP17208567.2A 2017-12-19 2017-12-19 Kompressorsteuerung Withdrawn EP3502438A1 (de)

Priority Applications (7)

Application Number Priority Date Filing Date Title
EP17208567.2A EP3502438A1 (de) 2017-12-19 2017-12-19 Kompressorsteuerung
EP18830177.4A EP3728816A1 (de) 2017-12-19 2018-12-12 Kompressorsteuerung
PCT/EP2018/084598 WO2019121252A1 (en) 2017-12-19 2018-12-12 Compressor control
US16/767,325 US11365690B2 (en) 2017-12-19 2018-12-12 Compressor control
RU2020120154A RU2744116C1 (ru) 2017-12-19 2018-12-12 Управление компрессором
CN201880082106.7A CN111527293B (zh) 2017-12-19 2018-12-12 压气机控制
CA3083332A CA3083332C (en) 2017-12-19 2018-12-12 Control of compressor having variable guide vanes

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP17208567.2A EP3502438A1 (de) 2017-12-19 2017-12-19 Kompressorsteuerung

Publications (1)

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EP3502438A1 true EP3502438A1 (de) 2019-06-26

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EP18830177.4A Pending EP3728816A1 (de) 2017-12-19 2018-12-12 Kompressorsteuerung

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EP (2) EP3502438A1 (de)
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CA (1) CA3083332C (de)
RU (1) RU2744116C1 (de)
WO (1) WO2019121252A1 (de)

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110182715A1 (en) * 2008-09-18 2011-07-28 Siemens Aktiengesellschaft Adjusting device for variable guide vanes and method of operation
US20160281611A1 (en) * 2015-03-26 2016-09-29 Rolls-Royce Plc Variable inlet guide vane scheduling

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4295784A (en) * 1979-09-26 1981-10-20 United Technologies Corporation Variable stator
US4718823A (en) * 1987-02-24 1988-01-12 United Technologies Corporation Pitch changing mechanism for fan blades
US4950129A (en) * 1989-02-21 1990-08-21 General Electric Company Variable inlet guide vanes for an axial flow compressor
FR2712250B1 (fr) 1993-11-10 1995-12-29 Hispano Suiza Sa Procédé et dispositif de commande de variation du pas des pales d'un rotor.
JP3482093B2 (ja) * 1997-01-31 2003-12-22 三菱重工業株式会社 ガスタービン圧縮機静翼可変装置
EP1840355A1 (de) * 2006-03-27 2007-10-03 ALSTOM Technology Ltd Verfahren zum Betrieb einer Gasturbinen-Kraftanlage
US9303565B2 (en) * 2012-06-29 2016-04-05 Solar Turbines Incorporated Method and system for operating a turbine engine
US10001066B2 (en) * 2014-08-28 2018-06-19 General Electric Company Rotary actuator for variable geometry vanes
US10519964B2 (en) * 2016-12-06 2019-12-31 General Electric Company System and method for turbomachinery rotor and blade prognostics and diagnostics
US11268436B2 (en) * 2017-05-31 2022-03-08 Volvo Truck Corporation Method and vehicle system using such method

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110182715A1 (en) * 2008-09-18 2011-07-28 Siemens Aktiengesellschaft Adjusting device for variable guide vanes and method of operation
US20160281611A1 (en) * 2015-03-26 2016-09-29 Rolls-Royce Plc Variable inlet guide vane scheduling

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CA3083332C (en) 2022-05-24
CA3083332A1 (en) 2019-06-27
CN111527293A (zh) 2020-08-11
WO2019121252A1 (en) 2019-06-27
US20210025336A1 (en) 2021-01-28
EP3728816A1 (de) 2020-10-28
CN111527293B (zh) 2023-04-21
US11365690B2 (en) 2022-06-21
RU2744116C1 (ru) 2021-03-02

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